An experimental program to demonstrate the effect of unsteady combustion processes in a combustion‐augmented jet flow is described. Characteristics of noise for several combustors, having different flame holders and several lengths, operating in a jet temperature range from 1100°C to 1500° and a jet Mach number range from 0.2 to 0.35 (jet exit velocity ranging between 400 and 800 ft/sec) are presented. Data were collected from six B&K14‐in.microphones positioned at an angular separation of 15°in a quadrant of 50‐ft radius from the 2‐in. diam nozzle exit. Kistler type 601 pressure transducers are mounted in the duct wall of the combustor which is held on a pylon 12 ft above the ground. The experimental data collected and analyzed to date shows a directivity pattern with a nearly circular pattern, which has a peak in the vicinity of 45° to 60° from the jet axis. Comparison of internal pressure fluctuations with the farfield noise shows many simularities in the spectrum, an observation which is verified by the strong cross correlation between the two signals. Combustor and flame holder geometry are found to affect the level and frequency content of the noise. [Supported by NASA grant.]